3056 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39–AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2014–0922; 

Directorate Identifier 2014–NM–156–AD. 

(a) Comments Due Date 

We must receive comments by March 7, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) and (c)(2) of 

this AD, certificated in any category, except 

those on which Airbus modification (mod) 

152637 has been embodied in production. 

(1) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes, 

all manufacturer serial numbers (MSN). 

(2) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes, all 

manufacturer serial numbers (MSN). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that 

fatigue cracking could appear at certain 

fastener locations in the longeron area below 

the emergency exit cut-outs. We are issuing 

this AD to detect and correct cracking at 

certain fastener locations in the longeron area 

below the emergency exit cut-outs, which 

could lead to failure of the fasteners and 

reduced structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification of Fastener Locations 

Before the accumulation of 48,000 total 

flight cycles or 96,000 total flight hours, 

whichever occurs first since the airplane’s 

first flight, modify the 8 fastener locations in 

the longeron area (stringer 20A) below the 

emergency exit cut-outs on both RH and LH 

sides, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1265, Revision 02, 

dated July 10, 2014. 

(h) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–53–1265, dated January 2, 

2013; or Airbus Service Bulletin A320–53– 

1265, Revision 01, dated July 2, 2013; which 

are not incorporated by reference in this AD. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0085, dated 

May 13, 2015, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0922-0002. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

You may view this referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on January 

5, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00699 Filed 1–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8469; Directorate 

Identifier 2014–NM–105–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.28 Mark 

1000, 2000, 3000, and 4000 airplanes. 

This proposed AD was prompted by a 

design review that revealed insufficient 

measures were taken to ensure the 

correct locking of the attachments of the 

fuel quantity tank units (FQTUs) in each 

wing tank. When an FQTU becomes 

loose, this could lead to insufficient 

clearance between the FQTU and the 

adjacent tank structure or other metal 

parts, and under certain conditions, 

create an ignition source inside the wing 

fuel vapor space. This proposed AD 

would require modifying the FQTUs by 

applying sealant to cover the nuts, 

washers, and stud ends at the FQTU 

attachments in each main wing tank. 

This proposed AD would also require 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3057 

revising the maintenance or inspection 

program, as applicable, by incorporating 

a fuel airworthiness limitation item and 

a critical design configuration control 

limitation (CDCCL). We are proposing 

this AD to prevent an ignition source in 

the wing fuel tank vapor space, which 

could result in a wing fuel tank 

explosion and consequent loss of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by March 7, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Fokker 

Services B.V., Technical Services Dept., 

P.O. Box 1357, 2130 EL Hoofddorp, the 

Netherlands; telephone +31 (0)88–6280– 

350; fax +31 (0)88–6280–111; email 

technicalservices@fokker.com; Internet 

http://www.myfokkerfleet.com. You may 

view this referenced service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8469; or in person at the Docket 

Operations office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2015–8469; Directorate Identifier 

2014–NM–105–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0106, dated May 7, 2014 

(referred to after this the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for all Fokker Services B.V. 

Model F.28 Mark 1000, 2000, 3000, and 

4000 airplanes. The MCAI states: 

Prompted by an accident . . ., the Federal 

Aviation Administration (FAA) published 

Special Federal Aviation Regulation (SFAR) 

88 [(66 FR 23086, May 7, 2001)], and the 

Joint Aviation Authorities (JAA) published 

Interim Policy INT/POL/25/12. 

The review conducted by Fokker Services 

on the Fokker F28 design, in response to 

these regulations, revealed that insufficient 

measures were taken to ensure the correct 

locking of the attachments of the Fuel 

Quantity Tank Units (FQTUs). When a FQTU 

becomes loose, this could lead to insufficient 

clearance between the FQTU and the 

adjacent tank structure or other metal parts 

and, under certain conditions, create an 

ignition source inside the wing fuel tank 

vapour space. 

This condition, if not detected and 

corrected, could result in a wing fuel tank 

explosion and consequent loss of the 

aeroplane. 

To address this potential unsafe condition, 

Fokker Services developed a modification to 

ensure that each FQTU remains properly 

attached. 

For the reasons described above, this 

[EASA] AD requires the application of 

sealant covering the nuts, washers and stud 

ends at the FQTU attachment in each wing 

tank [and a revision to the maintenance or 

inspection program, as applicable to 

incorporate a fuel airworthiness limitation 

item and a CDCCL]. More information on this 

subject can be found in Fokker Services All 

Operators Message AOF28.038#02. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8469. 

The FAA has examined the 

underlying safety issues involved in fuel 

tank explosions on several large 

transport airplanes, including the 

adequacy of existing regulations, the 

service history of airplanes subject to 

those regulations, and existing 

maintenance practices for fuel tank 

systems. As a result of those findings, 

we issued a regulation titled ‘‘Transport 

Airplane Fuel Tank System Design 

Review, Flammability Reduction and 

Maintenance and Inspection 

Requirements’’ (66 FR 23086, May 7, 

2001). In addition to new airworthiness 

standards for transport airplanes and 

new maintenance requirements, this 

rule included Special Federal Aviation 

Regulation No. 88 (‘‘SFAR 88,’’ 

Amendment 21–78, and subsequent 

Amendments 21–82 and 21–83). 

Among other actions, SFAR 88 (66 FR 

23086, May 7, 2001) requires certain 

type design (i.e., type certificate (TC) 

and supplemental type certificate (STC)) 

holders to substantiate that their fuel 

tank systems can prevent ignition 

sources in the fuel tanks. This 

requirement applies to type design 

holders for large turbine-powered 

transport airplanes and for subsequent 

modifications to those airplanes. It 

requires them to perform design reviews 

and to develop design changes and 

maintenance procedures if their designs 

do not meet the new fuel tank safety 

standards. As explained in the preamble 

to the rule, we intended to adopt 

airworthiness directives to mandate any 

changes found necessary to address 

unsafe conditions identified as a result 

of these reviews. 

In evaluating these design reviews, we 

have established four criteria intended 

to define the unsafe conditions 

associated with fuel tank systems that 

require corrective actions. The 

percentage of operating time during 

which fuel tanks are exposed to 

flammable conditions is one of these 

criteria. The other three criteria address 

the failure types under evaluation: 

Single failures, single failures in 

combination with a latent condition(s), 

and in-service failure experience. For all 

four criteria, the evaluations included 

consideration of previous actions taken 

that may mitigate the need for further 

action. 


tkelley on DSK3SPTVN1PROD with PROPOSALS
3058 Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 

The Joint Aviation Authorities (JAA) 

has issued a regulation that is similar to 

SFAR 88 (66 FR 23086, May 7, 2001). 

(The JAA is an associated body of the 

European Civil Aviation Conference 

(ECAC) representing the civil aviation 

regulatory authorities of a number of 

European States who have agreed to cooperate in developing and 

implementing common safety regulatory 

standards and procedures.) Under this 

regulation, the JAA stated that all 

members of the ECAC that hold type 

certificates for transport category 

airplanes are required to conduct a 

design review against explosion risks. 

We have determined that the actions 

identified in this AD are necessary to 

reduce the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. 

Related Service Information Under 1 

CFR Part 51 

Fokker Services B.V. has issued 

Fokker Service Bulletin SBF28–28–054, 

Revision 1, which includes Fokker 

Manual Change Notification MCNM– 

F28–037, Revision 1, dated January 9, 

2014. The service information describes 

procedures for applying sealant to the 

attachment nuts, washers, and stud ends 

of the FQTU. 

Fokker Services B.V. has also issued 

Fokker Service Bulletin SBF28–28–050, 

Revision 3, dated December 11, 2014. 

The service information describes the 

fuel airworthiness limitation item and 

the CDCCL. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of these same 

type designs. 

This AD requires revisions to certain 

operator maintenance documents to 

include new actions (e.g., inspections) 

and/or CDCCLs. Compliance with these 

actions and/or CDCCLs is required by 14 

CFR 91.403(c). For airplanes that have 

been previously modified, altered, or 

repaired in the areas addressed by this 

AD, the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (k)(1) of this proposed AD. 

The request should include a 

description of changes to the required 

actions that will ensure the continued 

operational safety of the airplane. 

Costs of Compliance 

We estimate that this proposed AD 

affects 5 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Modification and maintenance program revision.7 work-hours × $85 per hour = $595 ............. $0 $595 $2,975 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Fokker Services B.V.: Docket No. FAA– 

2015–8469; Directorate Identifier 2014– 

NM–105–AD. 

(a) Comments Due Date 

We must receive comments by March 7, 

2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model F.28 Mark 1000, 2000, 3000, and 4000 

airplanes, certificated in any category, all 

serial numbers. 


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Federal Register / Vol. 81, No. 12 / Wednesday, January 20, 2016 / Proposed Rules 3059 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Reason 

This AD was prompted by a design review 

that revealed insufficient measures were 

taken to ensure the correct locking of the 

attachments of the fuel quantity tank units 

(FQTUs) in each wing tank. When an FQTU 

becomes loose, this could lead to insufficient 

clearance between the FQTU and the 

adjacent tank structure or other metal parts, 

and under certain conditions, create an 

ignition source inside the wing fuel vapor 

space. We are issuing this AD to prevent an 

ignition source in the wing fuel tank vapor 

space, which could result in a wing fuel tank 

explosion and consequent loss of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification of the FQTUs 

At the next scheduled opening of the fuel 

tanks after the effective date of this AD, but 

no later than 84 months after the effective 

date of this AD, modify the FQTU in each 

main wing tank by applying sealant to cover 

the nuts, washers, and stud ends of the FQTU 

attachments, and do an inspection for leakage 

of the tank access panels, in accordance with 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–054, Revision 1, 

including Fokker Manual Change 

Notification MCNM–F28–037, Revision 1, 

dated January 9, 2014. If any fuel leakage is 

found, before further flight, reapply the 

sealant, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF28–28–054, Revision 1, 

including Fokker Manual Change 

Notification MCNM–F28–037, Revision 1, 

dated January 9, 2014. 

(h) Revision of Maintenance or Inspection 

Program 

Before further flight after completing the 

modification specified in paragraph (g) of 

this AD, or within 30 days after the effective 

date of this AD, whichever occurs later: 

Revise the airplane maintenance or 

inspection program, as applicable, by 

incorporating the fuel airworthiness 

limitation item and critical design 

configuration control limitation (CDCCL) 

specified in paragraph 1.L.(1)(c) of Fokker 

Service Bulletin SBF28–28–054, Revision 1, 

dated January 9, 2014. The initial compliance 

times for these tasks are at the latest of the 

times specified in paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD. 

(1) At the applicable time specified in 

Fokker Service Bulletin SBF28–28–050, 

Revision 3, dated December 11, 2014. 

(2) Before further flight after completing 

the modification specified in paragraph (g) of 

this AD. 

(3) Within 30 days after the effective date 

of this AD. 

(i) No Alternative Actions, Intervals, and 

CDCCLs 

After accomplishing the revision required 

by paragraph (h) of this AD, no alternative 

actions (e.g., inspections), intervals, or 

CDCCLs may be used unless the actions, 

intervals, or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (k)(1) of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Fokker Service Bulletin 

SBF28–28–054, dated June 30, 2010, which 

is not incorporated by reference in this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Fokker B.V. Service’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0106, dated 

May 7, 2014, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov. by 

searching for and locating Docket No. FAA– 

2015–8469. 

(2) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 1357, 

2130 EL Hoofddorp, the Netherlands; 

telephone +31 (0)88–6280–350; fax +31 

(0)88–6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.com. You may view this 

service information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on January 

6, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–00637 Filed 1–19–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8466; Directorate 

Identifier 2015–NM–045–AD] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.28 Mark 

0070 and 0100 airplanes. This proposed 

AD was prompted by the need for more 

restrictive fuel airworthiness 

limitations. This proposed AD would 

require revising the maintenance 

program or inspection program, as 

applicable, to incorporate certain fuel 

system airworthiness limitations. We 

are proposing this AD to reduce the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: We must receive comments on 

this proposed AD by March 7, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 


tkelley on DSK3SPTVN1PROD with PROPOSALS